Battery structural assembly

1. An aircraft comprising:

(a) a fuselage;

(b) an airframe supporting the fuselage, wherein the airframe includes a pair of longitudinally-extending beams; and

(c) a pair of adjacent battery assemblies, each battery assembly of the pair of adjacent battery assemblies including:

(i) a cold plate secured to the pair of longitudinally-extending beams such that the cold plate is configured to act as a load path for the airframe, the cold plate including an attachment flange, and

(ii) a battery mounted to the cold plate,

wherein the respective cold plates of the pair of adjacent battery assemblies are secured to each other via the respective attachment flanges.

2. The aircraft of claim 1 , wherein the cold plate includes:

(a) a planar member; and

(b) at least one fluid channel positioned below a lower side of the planar member and configured to receive a cooling fluid,

wherein the battery is mounted to an upper side of the planar member for transferring heat from the battery to the cooling fluid through the planar member.

3. The aircraft of claim 2 , wherein the planar member includes a main structural web.

4. The aircraft of claim 2 , wherein the cold plate further includes a plurality of stiffeners positioned on the upper side of the planar member.

5. The aircraft of claim 4 , wherein the plurality of stiffeners are spaced apart from each other to define respective compartments for receiving corresponding battery packs of the battery.

6. The aircraft of claim 2 , wherein the at least one fluid channel is defined by a tube extending along a lower recessed surface of the planar member.

7. The aircraft of claim 2 , wherein the cold plate further includes an enclosure panel operatively coupled to the planar member.

8. The aircraft of claim 7 , wherein the enclosure panel is positioned below the at least one fluid channel.

9. The aircraft of claim 8 , wherein the enclosure panel defines an outer structural skin of the aircraft.

10. The aircraft of claim 1 , wherein the battery includes a fitting having a plurality of apertures arranged in a grid pattern and configured to receive corresponding battery packs.

11. The aircraft of claim 10 , wherein the fitting is configured to clamp the battery packs against the cold plate.

12. The aircraft of claim 1 , wherein the attachment flange is configured to couple to the pair of longitudinally-extending beams.

13. The aircraft of claim 1 , wherein the battery has a battery weight, wherein the cold plate is configured to support the battery weight.

14. The aircraft of claim 1 , wherein the pair of longitudinally-extending beams includes a pair of upper roof beams.

15. The aircraft of claim 1 , wherein the pair of longitudinally-extending beams includes a pair of lower keel beams.

16. A method of manufacturing a battery assembly for an aircraft, the method comprising:

(a) positioning at least one tube defining at least one fluid channel below a main structural web of a first cold plate of a first battery assembly;

(b) operatively coupling a battery to the main structural web such that the battery is positioned above the at least one fluid channel and such that the battery is spaced apart from the at least one tube by the main structural web;

(c) securing the main structural web to a pair of beams of the aircraft such that the battery remains above the at least one fluid channel; and

(d) securing the first cold plate to a second cold plate of a second battery assembly adjacent to the first battery assembly, via a first attachment flange of the first cold plate and a second attachment flange of the second cold plate.

17. An aircraft comprising:

(a) a fuselage;

(b) an airframe supporting the fuselage, wherein the airframe includes a pair of longitudinally-extending beams; and

(c) at least one battery assembly, each of the at least one battery assembly (c) including:

(i) a cold plate comprising:

(A) a main structural web,

(B) a plurality of stiffeners positioned on an upper side of the main structural web,

(C) at least one attachment flange coupled to the pair of longitudinally-extending beams, and

(ii) a battery mounted to the cold plate, wherein the battery has a weight and is configured to apply a bending load to the cold plate,

wherein the cold plate is configured to transfer at least a portion of the bending load through the plurality of stiffeners, the main structural web, and the at least one attachment flange to the pair of longitudinally-extending beams,

wherein the at least one battery assembly includes a pair of adjacent battery assemblies, wherein the respective cold plates of the pair of adjacent battery assemblies are secured to each other via the respective attachment flanges.

18. The aircraft of claim 17 , wherein the cold plate is further configured to react shear loads.